Abstract: Described herein is an aircraft. The aircraft comprises a body. The aircraft also comprises a wing coupled to and extending from the body. The wing comprises a wing inboard end portion, a wing outboard end portion, opposite the wing inboard end portion, and an intermediate portion between the wing inboard end portion and the wing outboard end portion. The aircraft further comprises a strut. The strut comprises a strut inboard end portion coupled to and extending from the body and a strut outboard end portion coupled to and extending from the intermediate portion of the wing. The aircraft additionally comprises at least one aerodynamic control surface movably coupled to the strut.

Abstract: Methods, apparatus, and articles of manufacture to extend a leading-edge vortex of a highly-swept wing aircraft wing are disclosed. An example apparatus includes a shoulder wing coupled to a fuselage of an aircraft above a highly-swept wing of the aircraft, the shoulder wing operative in a first position to extend a leading-edge vortex spanwise along the highly-swept wing of the aircraft.

Abstract: An aircraft includes a body, a wing coupled to and extending from the body, and a strut. The wing includes a wing thickest region bounded by a wing thickest region leading boundary and a wing thickest region trailing boundary. The strut includes a strut thickest region bounded by a strut thickest region leading boundary and a strut thickest region trailing boundary. In a planform view, the wing thickest region overlaps the strut thickest region at an overlap region, where the overlap region including less than fifteen percent of the strut thickest region.

Abstract: An aircraft that comprises a body, a wing, and a strut. The wing is coupled to and extends from the body. The wing comprises a wing inboard end portion, a wing outboard end portion, opposite the wing inboard end portion, and an intermediate portion between the wing inboard end portion and the wing outboard end portion. The strut comprises a strut inboard end portion and a strut outboard end portion. The strut inboard end portion is coupled to and extends from the body and the strut outboard end portion is coupled to and extends from the intermediate portion of the wing. The strut outboard end portion of the strut is configured to generate a download acting on the strut outboard end portion of the strut when the aircraft is in flight.

Abstract: Disclosed herein is an aircraft that comprises a body, a wing, and a strut. The wing is coupled to and extends from the body. A strut inboard end portion is coupled to and extends from the body and a strut outboard end portion is coupled to and extends from an intermediate portion of the wing. The wing further comprises a first thinned portion adjacent the intermediate portion of the wing. An overall thickness of the first thinned portion of the wing decreases and increases in a spanwise direction along the wing. The strut further comprises a second thinned portion adjacent the outboard end portion of the strut. An overall thickness of the second thinned portion of the strut decreases and increases in a spanwise direction along the strut.

Abstract: An aircraft includes a body, a wing coupled to and extending from the body, and a strut. The wing includes a wing thickest region bounded by a wing thickest region leading boundary and a wing thickest region trailing boundary. The strut includes a strut thickest region bounded by a strut thickest region leading boundary and a strut thickest region trailing boundary. In a planform view, the wing thickest region overlaps the strut thickest region at an overlap region, where the overlap region including less than fifteen percent of the strut thickest region.

Abstract: Described herein is an aircraft. The aircraft comprises a body. The aircraft also comprises a wing coupled to and extending from the body. The wing comprises a wing inboard end portion, a wing outboard end portion, opposite the wing inboard end portion, and an intermediate portion between the wing inboard end portion and the wing outboard end portion. The aircraft further comprises a strut. The strut comprises a strut inboard end portion coupled to and extending from the body and a strut outboard end portion coupled to and extending from the intermediate portion of the wing. The aircraft additionally comprises at least one aerodynamic control surface movably coupled to the strut.

Abstract: An aircraft that comprises a body, a wing, and a strut. The wing is coupled to and extends from the body. The wing comprises a wing inboard end portion, a wing outboard end portion, opposite the wing inboard end portion, and an intermediate portion between the wing inboard end portion and the wing outboard end portion. The strut comprises a strut inboard end portion and a strut outboard end portion. The strut inboard end portion is coupled to and extends from the body and the strut outboard end portion is coupled to and extends from the intermediate portion of the wing. The strut outboard end portion of the strut is configured to generate a download acting on the strut outboard end portion of the strut when the aircraft is in flight.

Abstract: Disclosed herein is an aircraft that comprises a body, a wing, and a strut. The wing is coupled to and extends from the body. A strut inboard end portion is coupled to and extends from the body and a strut outboard end portion is coupled to and extends from an intermediate portion of the wing. The wing further comprises a first thinned portion adjacent the intermediate portion of the wing. An overall thickness of the first thinned portion of the wing decreases and increases in a spanwise direction along the wing. The strut further comprises a second thinned portion adjacent the outboard end portion of the strut. An overall thickness of the second thinned portion of the strut decreases and increases in a spanwise direction along the strut.

Abstract: Methods, apparatus, and articles of manufacture to extend a leading-edge vortex of a highly-swept wing aircraft wing are disclosed. An example apparatus includes a shoulder wing coupled to a fuselage of an aircraft above a highly-swept wing of the aircraft, the shoulder wing operative in a first position to extend a leading-edge vortex spanwise along the highly-swept wing of the aircraft.

Abstract: A vortex generator may include a depression in an aerodynamic surface, and a vortex generator leading edge located in the depression. The vortex generator leading edge may include a leading edge upper surface. The leading edge upper surface may be positioned at or below a tangent line defined at a location along the aerodynamic surface upstream of the depression relative to an oncoming local flow.

Abstract: A vortex generator may include a depression in an aerodynamic surface, and a vortex generator leading edge located in the depression. The vortex generator leading edge may include a leading edge upper surface. The leading edge upper surface may be positioned at or below a tangent line defined at a location along the aerodynamic surface upstream of the depression relative to an oncoming local flow.

Abstract: A retractable chine assembly includes at least one chine which is hingebly mountable to a surface such as of an aircraft having a wing. The chine is preferably configured to be movable between stowed and deployed positions. The aircraft may include an engine nacelle which may be mounted on an underside of the wing. The nacelle may generate a nacelle wake that passes over the wing upper surface at high angles of attack and induces flow separation. The chine is preferably configured such that a vortex generated thereby interacts which the nacelle wake to delay flow separation and stall.

Abstract: A retractable chine assembly includes at least one chine which is hingebly mountable to a surface such as of an aircraft having a wing. The chine is preferably configured to be movable between stowed and deployed positions. The aircraft may include an engine nacelle which may be mounted on an underside of the wing. The nacelle may generate a nacelle wake that passes over the wing upper surface at high angles of attack and induces flow separation. The chine is preferably configured such that a vortex generated thereby interacts which the nacelle wake to delay flow separation and stall.